Aug 23, 2002 - St. Etienne du Rouvray, France. The investigation of the shock-wave structure and numerical characteristics of supersonic- jet shear layer is of ...
AN EXPERIMENTAL AND NUMERICAL STUDY OF A SUPERSONIC-JET SHOCK-WAVE STRUCTURE V.I. Zapryagaev1, A.N. Kudryavtsev1, A.V. Lokotko1, A.V. Solotchin1, A.A. Pavlov1, and A. Hadjadj2 1
Institute of Theoretical and Applied Mechanics, Siberian Branch, 630090 Novosibirsk, Russia 2 LMFN-CORIA, UMR CNRS 6614, INSA de Rouen, St. Etienne du Rouvray, France
The investigation of the shock-wave structure and numerical characteristics of supersonicjet shear layer is of great importance due to numerous applications of supersonic jets in aerospace engineering. In the present work, a detailed study of a supersonic non-isobaric jet aimed at validation and further development of numerical algorithms for jet flow prediction has been carried out. The difficulties in numerical simulation of supersonic non-isobaric jets stem from the necessity of accurate resolution of various flow scales and from the occurrence of multiple shock waves and subsonic pockets interacting with each other. Although the literature [1, 2] contains many data on the structure of supersonic underexpanded jet flows, accurate verification of numerical predictions requires detailed measurements of the jet structure to be performed at a precise control over supersonic nozzle geometry and jet flow parameters. The experiments were performed in the jet facility of the Institute of Theoretical and Applied Mechanics (Novosibirsk) operating on cold air (specific heat ratio γ=1.4, stagnation temperature To=287 K). The jet was exhausted into quiescent air with the ambient pressure Ph=1.008 bar and ambient temperature Th=294 K. The setup (Fig. 1) was a vertically installed plenum chamber with a nozzle fixture assembly provided at center of its head. The inner diameter of the compression chamber, which housed a honeycomb and settling grids, was 330 mm. The inlet diameter of the air pipeline
Fig. 1. Scheme of the jet facility used, 1 – nozzle, 2 – Pitot probe, 3 – traversing gear. © V.I. Zapryagaev, A.N. Kudryavtsev, A.V. Lokotko, A.V. Solotchin, A.A. Pavlov, and A. Hadjadj, 2002
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Report Documentation Page Report Date 23 Aug 2002
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Title and Subtitle An Experimental and Numerical Study of A Supersonic-Jet Shock-Wave Structure
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Performing Organization Name(s) and Address(es) Institute of Theoretical and Applied Mechanics Institutskaya 4/1 Novosibirsk 530090 Russia
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Distribution/Availability Statement Approved for public release, distribution unlimited Supplementary Notes See also ADM001433, Conference held International Conference on Methods of Aerophysical Research (11th) Held in Novosibirsk, Russia on 1-7 Jul 2002 Abstract Subject Terms Report Classification unclassified
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through which the air was supplied to the nozle was 88 mm. The setup was equipped with a traversing gear that allowed us to scan the flow with a Pitot probe both in streamwise and radial directions (in the interval of respective cylindrical coordinates 0< x < 720 mm and 0< r 30). The radial pressure profile becomes self-similar (see Fig. 6). The peak pressure in the maximum at the axis exerts distinct oscillations. To measure the radial pressure profiles at x/Ra>30, we used two identical Pitot probes spaced apart by 30 mm. In Figure 6, the indications of the inner and outer pressure probes are shows with circles and triangles, respectively. In the region where the data measured by the both probes are available, these data are seen to be in a fairly good agreement. Within the framework of the present study, numerical simulations of the nozzle and jet flows were carried out. Their first results will be discussed at the presentation. Conclusions Detailed experimental data of a complex study of the flow structure of air supersonic over-expanded jet exhausted from an axisymmetric conical nozzle into drowned space have been presented. These data may prove useful in verifying numerical algorithms for predicting the shock-wave structure of supersonic non-isobaric gas jets. Acknowledgement. This research was supported by INTAS under the Grant No. 99-0785. REFERENCES 1. 2. 3. 4.
Avduevsky V.S., Ashratov E.A., Ivanov A.V., Pirumov U.G. Gasdynamics of Supersonic Nonisobaric Jets. Moscow: Mashinostroenie, 1989. 320 p. (in Russian). S.M.Dash. Analysis of exhaust plumes and their interaction with missile airframes. In book “Tactical missile aerodynamics”. Edited by M.J.Hemsch & J.N.Nielsen. AIAA, Inc., N.Y., (778-850) (1986). Glaznev V.N., Zapryagaev V.I., Uskov V.N. and all. Jet and Nonstationary Flows in Gasdanamics. Novosibirsk: Publishing Firm of Siberian Branch of Russian Academy of Sciences, 200 p., (2000) (in Russian). Zapryagaev V.I., Solotchin A.V. Evolution of Streamwise Vortices at the Initial Part of a Supersonic Nonisobaric Jet in the Presence of Microroughnesses of the Internal Surface of the Nozzle. Fluid Dynamics 32. No. 3, 465−469, (1997).
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